Aircraft Display Panel Bonding System

ABSTRACT

A method and apparatus for conforming a display panel to a surface of an aircraft structure. The method positions the display panel within a resin barrier that is located on the surface such that a cavity is formed, places a film and the display panel together, and applies a force on the display panel that causes the display panel to conform to the surface of the aircraft structure. The display panel has a shape that changes to a first shape to match a second shape of the surface of the aircraft structure. The method also injects a resin into the cavity while the force is applied, and cures the resin in the cavity while the force is applied to form a cured resin. The cured resin holds the display panel in the first shape and attaches the display panel to the surface of the aircraft structure.

BACKGROUND INFORMATION

1. Field

The present disclosure relates generally to aircraft and, in particular,to displaying information on an aircraft. Still more particularly, thepresent disclosure relates to a method and apparatus for displayinginformation on the exterior of an aircraft.

2. Background

Advertisements and other messages are typically placed in advertisingspaces in fixed locations. Advertisements are commonly found onbillboards, buildings, and other structures. Advertisers have includedother systems, other than those in fixed locations, for increasing thevisibility of advertisements and other messages.

For example, advertisements are often placed on moving vehicles. Thesevehicles include buses, taxicabs, airplanes, and other suitable types ofvehicles. In some cases, trucks have been used solely for the purpose ofacting as a mobile billboard. With advertisements on vehicles, theseadvertisements can be seen in many more areas than may otherwise bepossible based on restrictions or costs for more traditional types ofadvertisements.

For example, advertisements may be painted on the surface of anaircraft. In other cases, the advertisements may be placed onto thesurface of an aircraft in the form of an appliqué. Some of theseappliqués may be in the form of aircraft display units attached to thesurface of the aircraft. Currently available display units include rigiddisplay panels that are attached to the surface of the aircraft. Thesedisplay panels may be attached to the surface of the aircraft using abonding material such as an adhesive.

When a location for a display panel has a curved surface, the aircraftdisplay system may be designed to include a display panel that is alsocurved. The curvature of the display panel, however, may vary from thecurvature of the surface of the aircraft. As a result, affixing adisplay panel on the surface of the aircraft may require the use of arigid tool that applies pressure to the aircraft display system in amanner that causes the display panel to conform to the curvature of thesurface of the aircraft.

Changing the shape of the display panel to have a desired curvature thatmatches the curvature of the surface of the aircraft in a desired mannerresults in stresses within the display panel, aircraft surface, or both.The stresses may reduce the life of either or both the display panel andthe aircraft structure. These stresses also may alter performance of theaircraft. In other cases, the stresses may result in a need formaintenance to reattach the display panel to the surface of theaircraft.

Therefore, it would be desirable to have a method and apparatus thattake into account at least some of the issues discussed above, as wellas other possible issues. For example, it would be desirable to have amethod and apparatus that overcome the technical problem of attachingdisplay panels to the surface of an aircraft in a manner that reducesstresses to the display panels attached to the surface of an aircraft.It would also be desirable to have a method and apparatus that overcomethe need for either or both secondary bonding and application offasteners.

SUMMARY

An embodiment of the present disclosure provides a method for conforminga display panel to a surface of an aircraft structure. The methodpositions the display panel within a resin barrier that is located onthe surface such that a cavity is formed and applies a force on thedisplay panel that causes the display panel to conform to the surface ofthe aircraft structure. The display panel has a shape that changes to afirst shape to match a second shape of the surface of the aircraftstructure. The method also injects a resin into the cavity while theforce is applied, and cures the resin in the cavity while the force isapplied to form a cured resin. The cured resin holds the display panelin the first shape and attaches the display panel to the surface of theaircraft structure.

Another embodiment of the present disclosure provides a method forconforming a display panel. The method positions the display panelwithin a resin barrier and against a surface of a structure such that abottom side of the display panel is against the surface of thestructure, places a resin into a cavity defined by the display panelpositioned within the resin barrier and against the surface of thestructure, applies a force on the display panel that is sufficient tocause spacing structures on the display panel to touch the surface ofthe structure such that the display panel has a shape that changes to afirst shape to match a second shape of the surface of the structure, andcures the resin while the force is applied to the display panel to forma cured resin that holds the display panel in the first shape.

Yet another embodiment of the present disclosure provides an apparatuscomprising a display panel, a film attached to a top side of the displaypanel, and a cured resin. The display panel has structures on a bottomside that are against a surface of an aircraft structure. The structurescause the display panel to have a desired shape when the structures areagainst the surface of the aircraft structure. The cured resin attachesthe display panel to the surface of the aircraft structure. The curedresin fills a cavity defined by the film, the display panel, the surfaceof the aircraft structure, and a resin barrier. The cured resin alsoholds the display panel in the desired shape.

The features and functions can be achieved independently in variousembodiments of the present disclosure or may be combined in yet otherembodiments in which further details can be seen with reference to thefollowing description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the illustrativeembodiments are set forth in the appended claims. The illustrativeembodiments, however, as well as a preferred mode of use, furtherobjectives and features thereof, will best be understood by reference tothe following detailed description of an illustrative embodiment of thepresent disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 is an illustration of a block diagram of an information displayenvironment in accordance with an illustrative embodiment;

FIG. 2 is an illustration of a block diagram of a display panel inaccordance with an illustrative embodiment;

FIG. 3 is an illustration of a block diagram of a process for attachinga display panel to a surface of an aircraft in accordance with anillustrative embodiment;

FIG. 4 is an illustration of an aircraft in accordance with anillustrative embodiment;

FIG. 5 is an illustration of an aircraft structure in accordance with anillustrative embodiment;

FIG. 6 is an illustration of preparing a wing to receive a display panelin accordance with an illustrative embodiment;

FIG. 7 is an illustration of positioning a display panel in accordancewith an illustrative embodiment;

FIG. 8A is an illustration of the positioning of a caul plate inaccordance with an illustrative embodiment;

FIG. 8B is an illustration of the placement of a syringe in a resinbarrier in accordance with an illustrative embodiment;

FIG. 9 is an illustration of a display panel attached to an aircraftstructure in accordance with an illustrative embodiment;

FIG. 10 is an illustration of a cross-section of a display panel inaccordance with an illustrative embodiment;

FIG. 11 is an illustration of a cross-section of a display panelpositioned on a resin barrier and an aircraft structure in accordancewith an illustrative embodiment;

FIG. 12 is an illustration of a cross-section of a display panelpositioned within a resin barrier and an aircraft structure with a forceapplied to the display panel in accordance with an illustrativeembodiment;

FIG. 13 is an illustration of a cross-section of resin in a cavity of adisplay panel while a force is applied to the display panel inaccordance with an illustrative embodiment;

FIG. 14 is an illustration of a cross-section of cured resin in a cavityof a display panel in accordance with an illustrative embodiment;

FIG. 15 is an illustration of mechanical attachment features inaccordance with an illustrative embodiment;

FIG. 16 is an illustration of a flowchart of a process for conforming adisplay panel in accordance with an illustrative embodiment;

FIG. 17 is an illustration of a flowchart of a process for conformingand attaching a display panel to the surface of an aircraft inaccordance with an illustrative embodiment;

FIG. 18 is an illustration of a flowchart of a process for applying aforce on a display panel in accordance with an illustrative embodiment;

FIG. 19 is an illustration of a block diagram of an aircraftmanufacturing and service method in accordance with an illustrativeembodiment; and

FIG. 20 is an illustration of a block diagram of an aircraft in which anillustrative embodiment may be implemented.

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account one or moredifferent considerations. For example, those embodiments recognize andtake into account that presently used techniques for attaching a rigiddisplay panel or semi-flexible display panel to the surface of anaircraft may result in the display panel having a shorter than desiredlife, not matching the shape of the surface of the aircraft, needingmaintenance for cleaning beneath the display panel, reattaching thedisplay panel to the surface of the aircraft, resealing the displaypanel, or some combination thereof.

The illustrative embodiments also recognize and take into account thatone solution may be to use a flexible display panel. The illustrativeembodiments recognize and take into account, however, that with flexibledisplay panels, wrinkles may be present on the display panels when theflexible display panels are attached to the surface of the aircraft.

Thus, the illustrative embodiments provide a method and apparatus formatch-forming and attaching a display panel to the surface of anaircraft. In the illustrative example, match-forming is a process inwhich a display panel changes shape. For example, the display panel maychange shape to conform to the surface of the structure. In one example,the display panel may change shape by bending such that a first surfaceof the display system matches a second surface of the structure on whichthe display panel is to be attached. The bending occurs along one ormore axes. In this manner, the first shape of the display panel matchesthe second shape of the structure through match-forming.

In one illustrative example, the display panel is attached to thesurface of an aircraft structure in a manner that reduces stress,wrinkling, or some combination thereof in the display panel. A resinbarrier is formed on a surface of the aircraft structure. The displaypanel is positioned on the resin barrier formed on the surface of theaircraft structure such that a bottom side of the display panel is incontact with the resin barrier. A resin is placed into a cavity definedby the, display panel, a caul plate and an aircraft surface. The displaypanel is within the resin barrier and positioned in between the caulplate and the aircraft surface on the resin barrier. A force is appliedon the display panel that is sufficient to cause spacing structures onthe display panel to touch the surface of the aircraft structure suchthat the display unit has a desired shape and finish.

The finish may be determined by the caul plate surface. For example, ifthe caul plate has a smooth surface, the resin at the top of the displaypanel may be smooth. If the caul plate has a pattern, the resin at thetop of the display panel may have the pattern. The resin is cured whilethe force is applied to the display panel to form a cured resin thatholds the display panel on the surface of the aircraft structure withthe first shape.

With reference now to the figures and, in particular, with reference toFIG. 1, an illustration of a block diagram of an information displayenvironment is depicted in accordance with an illustrative embodiment.In this illustrative example, information display environment 100includes vehicle 102 in the form of aircraft 104.

In this illustrative example, information 106 is displayed on aircraft104 using display system 108. As depicted, display system 108 is incommunication with computer system 110 and comprises a number of displaypanels 112. As used herein, a “number of,” when used with reference toitems, means one or more items. For example, a number of display panels112 is one or more of display panels 112.

As depicted, computer system 110 is a hardware system that includes oneor more data processing systems located in aircraft 104. When more thanone data processing system is present, those data processing systems maybe in communication with each other using a communications medium. Thecommunications medium may be a network. Further, computer system 110 isin communication with display system 108 using the communicationsmedium. The data processing systems may be selected from at least one ofa computer, a server computer, a workstation, a tablet computer, alaptop computer, an electronic flight bag, a mobile phone, some othersuitable data processing system, an aircraft device, a cockpit interfacedevice, or avionics gear.

As depicted, computer system 110 identifies information 106, generatesinformation 106, or some combination thereof. Computer system 110 maysend information 106 to display system 108 for display on surface 114 ofaircraft 104 by the number of display panels 112. In this illustrativeexample, surface 114 is a surface on structure 113 in the form ofaircraft structure 115 when vehicle 102 is aircraft 104.

In the illustrative example, surface 114 is selected from at least oneof exterior surface 116 or interior surface 118. As depicted, one ormore of display panels 112 may be located on at least one of exteriorsurface 116 or interior surface 118 of aircraft 104.

As used herein, the phrase “at least one of,” when used with a list ofitems, means different combinations of one or more of the listed itemsmay be used and only one of each item in the list may be needed. Inother words, “at least one of” means any combination of items and numberof items may be used from the list, but not all of the items in the listare required. The item may be a particular object, thing, or a category.

For example, without limitation, “at least one of item A, item B, oritem C” may include item A, item A and item B, or item B. This examplealso may include item A, item B, and item C or item B and item C. Ofcourse, any combinations of these items may be present. In someillustrative examples, “at least one of” may be, for example, withoutlimitation, two of item A; one of item B; and ten of item C; four ofitem B and seven of item C; or other suitable combinations.

In the illustrative example, information 106 may be displayed indifferent forms. For example, information 106 may be advertisements,flight information, ground crew information, an airline logo, a warning,or other suitable information depending on whether information 106 isdisplayed on exterior surface 116 or interior surface 118 of aircraft104.

As depicted, display panel 120 in the number of display panels 112 isattached to surface 114 of aircraft structure 115 for aircraft 104. Theattachment is such that display panel 120 is substantially flush toexterior surface 116 of aircraft 104 when display panel 120 is attachedto exterior surface 116 of aircraft 104.

For example, if exterior surface 116 of aircraft 104 is substantiallyflat, display panel 120 maintains the substantially flat surface forexterior surface 116 of aircraft 104. If exterior surface 116 ofaircraft 104 has a curve, display panel 120 at that location has asimilar curve such that display panel 120 maintains the curve as desiredfor the aircraft.

In other words, display panel 120 may be considered part of exteriorsurface 116 for performance purposes of aircraft 104. In this manner,the aerodynamic properties for exterior surface 116 of aircraft 104 mayremain at a desired level of performance.

With reference now to FIG. 2, an illustration of a block diagram of adisplay panel is depicted in accordance with an illustrative embodiment.As depicted, display panel 120 is a hardware device that is configuredto display information 106 in FIG. 1. Information 106 may be, forexample, an image. In the illustrative examples, the same referencenumeral may be used in more than one figure. This reuse of a referencenumeral in different figures represents the same element in thedifferent figures.

In this illustrative example, display panel 120 may be implemented usinga number of different types of display technologies. For example,display panel 120 may be selected from at least one of a light-emittingdiode display, an organic light-emitting diode display, a plasmadisplay, a quantum dot display, a liquid crystal display, or othersuitable types of display devices. For example, other types ofelectroluminescent display devices may be used.

An example of components that may be used to implement display panel 120is depicted in FIG. 2. In this illustrative example, display panel 120includes substrate 200, electronic components 202, and spacingstructures 204.

As depicted, substrate 200 is flexible substrate 206. Substrate 200 isflexible in a number of axes. For example, substrate 200 may be flexibleon one axis, two axes, or some other number of axes.

In the illustrative example, substrate 200 may be designed to conform toa desired shape or flex during use. This conformance of substrate 200 tothe desired shape or flexing of substrate 200 during use occurs withoutundesired stresses that may result in cracking, erosion, discoloration,weathering, debonding, or other undesired conditions.

Substrate 200 may be formed using various types of substrates forcircuits including those used for flexible printed circuits. Forexample, substrate 200 may be implemented using a flexible plastic, apolyamide film, a transparent conductive polyester film, a polyetherether ketone (PEEK) substrate, or some other suitable type of substrate.

Substrate 200 may be comprised of a number of portions 208. When morethan one portion is present in the number of portions 208, thoseportions may be connected to each other. For example, the number ofportions 208 may take the form of a number of strips, squares,rectangles, or other suitable shapes.

In the illustrative example, electronic components 202 are associatedwith substrate 200. In some illustrative examples, electronic components202 and their connections may form substrate 200.

When one component is “associated” with another component, theassociation is a physical association in the depicted examples. Forexample, a first component, an electronic component in electroniccomponents 202, may be considered to be physically associated with asecond component, substrate 200, by at least one of being secured to thesecond component, bonded to the second component, mounted to the secondcomponent, welded to the second component, fastened to the secondcomponent, or connected to the second component in some other suitablemanner. The first component also may be connected to the secondcomponent using a third component. The first component may also beconsidered to be physically associated with the second component bybeing formed as a part of the second component, an extension of thesecond component, or both.

In this illustrative example, electronic components 202 includelight-emitting elements 210. As depicted, light-emitting elements may beselected from at least one of a light-emitting diode, an organiclight-emitting diode, a plasma cell, a liquid crystal cell, an infraredtransmitter, an ultraviolet light transmitter, or some other suitableelectroluminescent component that emits light. Electronic components 202may also include other components, such as video control circuits,communications circuits, or other suitable electronic components for usein display panel 120.

As depicted, electronic components 202 may be in the form of a chipwithin a case. The case may be a package that encapsulates, seals, orencapsulates and seals the chip as currently used in integratedcircuits. In some illustrative examples, the resin used with displaypanel 120 may function as the case or package.

Spacing structures 204 are structures associated with substrate 200.Spacing structures 204 may contact surface 114 when installing displaypanel 120 on surface 114 of aircraft structure 115. In some illustrativeexamples, spacing structures 204 may include some or all of electroniccomponents 202. In other words, electronic components 202 may alsofunction as spacing structures 204 in some illustrative examples.Spacing structures 204 are used to define the shape of display panel 120when display panel 120 is attached to surface 114.

Display panel 120 may include other components not shown. For example,electrical connections between electronic components 202 may also bepresent.

Turning to FIG. 3, an illustration of a block diagram of a process forattaching a display panel to a surface of an aircraft is depicted inaccordance with an illustrative embodiment. As depicted, display panel120 may be attached to surface 114 of aircraft structure 115. Theattachment may be made in a manner that reduces stress, maintenance, andother undesired conditions that occur with currently used displaypanels.

In this illustrative example, resin barrier 300 is formed on surface114. Resin barrier 300 is a barrier for resin 306. As depicted, resinbarrier 300 includes perimeter wall 301 and surface layer 303.

In the illustrative example, perimeter wall 301 is configured tosurround display panel 120. Surface layer 303 is located within aperimeter defined by perimeter wall 301. In some illustrative examples,surface layer 303 may be omitted. In this illustrative example, resinbarrier 300 is a material selected from at least one of a polymer, aninsulating polymer, a film adhesive, a gel coat, an elastomer, aninsulating elastomer, a primer, or some other suitable material.

Display panel 120 is placed within resin barrier 300 as formed onsurface 114 of aircraft structure 115. In other words, display panel 120is placed inside of perimeter wall 301 when display panel 120 is placedwithin resin barrier 300. Display panel 120 is placed together withsurface layer 303 within the wall of perimeter wall 301. The placementof display panel 120 such that bottom side 302 of display panel 120 isin contact with resin barrier 300. In this illustrative example, cavity304 is defined by display panel 120 positioned on resin barrier 300.Caul plate 320 may be positioned on display panel 120. For example,bottom side 302 of display panel 120, resin barrier 300, and surface 114encompassed by resin barrier 300 may define cavity 304.

As depicted, resin 306 is placed into cavity 304. For example, resin 306may be injected into cavity 304 using an injection device such as asyringe, an end effector on a robotic arm, a vacuum pump, or some othersuitable device. The injection may be made by inserting the injectiondevice through resin barrier 300. In another illustrative example, avalve may be formed within resin barrier 300 to allow for placement ofresin 306 into cavity 304.

As depicted, resin 306 is a resin that holds or maintains display panel120 in first shape 308 after resin 306 is cured. Additionally, resin 306may be selected from a resin that will bond or otherwise attach displaypanel 120 to surface 114. For example, resin 306 may be selected from atleast one of a substantially transparent resin, a thermoset resin, anepoxy, a polyimide, a polyurethane, a silicone, an acrylic, a phenolic,or some other suitable material.

In addition to attaching display panel 120 to surface 114, resin 306also may function to seal display panel 120. Further, resin 306 also mayencapsulate electronic components 202.

Force 310 is applied to top side 312 of display panel 120 such thatdisplay panel 120 conforms to surface 114 of aircraft structure 115. Inthis illustrative example, force 310 may be applied perpendicular tosurface 114 of aircraft structure 115 over the area of surface 114. Forexample, force 310 may be in the form of a pressure. Force 310 in theform of pressure may be generated by applying a vacuum within the cavityor from an exterior source.

In this illustrative example, when force 310 is applied to display panel120, display panel 120 bends and spacing structures 204 contact surface114. In the illustrative example, when display panel 120 bends, thebending may be along one or more axes. The bending occurs such thatwrinkles in display panel 120 are reduced or avoided. In other words,display panel 120 changes shape in a manner that conforms to surface 114of aircraft structure 115.

The contact of spacing structures 204 causes substrate 200 in displaypanel 120 to bend such that display panel 120 has a shape that changesto first shape 308. Thus, the shape, size, number, and location ofspacing structures 204 may be selected to obtain first shape 308 thatmatches second shape 314 when force 310 is applied causing first shape308 to change to match second shape 314.

For example, force 310 is applied to top side 312 of display panel 120that is sufficient to cause spacing structures 204 on bottom side 302 ofdisplay panel 120 to touch surface 114 of aircraft structure 115.Spacing structures 204 touching surface 114 causes display panel 120 tohave first shape 308.

In this depicted example, display panel 120 is a flexible display panelthat bends to have first shape 308 that is substantially the same assecond shape 314 of surface 114 without an undesired amount of stressimparted within display panel 120. In other words, bending display panel120 does not cause stresses inside of display panel 120 that wouldresult in inconsistencies in substrate 200 that may require placement orrepair of substrate 200 sooner than expected or desired.

As depicted, first shape 308 of display panel 120 substantially conformsto second shape 314 of surface 114. For example, if second shape 314 ofsurface 114 is a curve, first shape 308 is also a curve. In theillustrative example, first shape 308 is the same or equal to secondshape 314 when the shapes are matched.

In this illustrative example, the location and configuration of spacingstructures 204 on bottom side 302 of display panel 120 are used todefine first shape 308 of display panel 120 when display panel 120 isattached to surface 114. The configuration may include the dimensions,materials, or other parameters for spacing structures 204.

Resin 306 is cured while force 310 is applied to display panel 120 toform cured resin 316 that holds display panel 120 on surface 114aircraft structure 115 with first shape 308. Cured resin 316 may attachdisplay panel 120 to surface 114 of aircraft structure 115. For example,resin 306 attaches display panel 120 to surface 114 by at least one offorming a bond to surface 114, mechanically securing display panel 120,or some other suitable combination of mechanisms. After resin 306 iscured, resin barrier 300 may be removed. Alternatively, resin barrier300 may remain in place.

When attached to surface 114 by cured resin 316, display panel 120 hasfirst shape 308 that substantially conforms to second shape 314 ofsurface 114. This type of attachment may be desirable when surface 114is exterior surface 116. First shape 308 may be such that a desiredairflow is present during operation of aircraft 104 when display panel120 is attached to exterior surface 116 such that display panel 120substantially conforms to exterior surface 116.

In the illustrative example, force 310 is applied through the use ofcaul plate 320. As depicted, caul plate 320 is semi-flexible. In otherwords, caul plate 320 may be flexible along at least one axis. Further,the flexibility of caul plate 320 is selected to be low enough such thatcaul plate 320 maintains a shape that is substantially similar to matchsecond shape 314 for exterior surface 116.

The flexibility of caul plate 320 is selected such that caul plate 320has a shape that contacts spacing structures 204 that may be located ontop side 312 of display panel 120. The contact is such that first shape308 for display panel 120 is a desired shape.

As depicted, caul plate 320 is positioned against top side 312 ofdisplay panel 120. Force 310 is applied to top side 312 of display panel120 through caul plate 320 that causes display panel 120 to conform tosurface 114 of aircraft structure 115. When film 318 is present on topside 312, caul plate 320 contacts film 318 as placed on display panel120.

Also, caul plate 320 has mating surface 324. In this illustrativeexample, mating surface 324 is the surface on caul plate 320 thatcontacts display panel 120 to apply force 310. Mating surface 324 mayinclude release layer 325 on mating surface 324. In the illustrativeexample, release layer 325 may be part of mating surface 324 or may be aseparate film. As depicted, release layer 325 may be formed from amaterial that provides properties selected from at least one ofanti-stick properties, inertness to chemicals used during manufacturing,or other suitable properties.

In one illustrative example, film 318 may be placed on display panel120. Film 318 may be substantially transparent. In some illustrativeexamples, portions of film 318 may have a nontransparent area for adesigner pattern. Film 318 may also provide electro-static chargedissipation.

Additionally, caul plate 320 may form physical features or pigmentedpatterns in film 318 through thermal mechanisms. The thermal mechanismmay be any curing system that generates heat to cure resin 306. Thethermal mechanisms applied to through caul plate 320 may also cure resin306. If film 318 is not present, caul plate 320 may form physicalfeatures or pigmented patterns in cured resin 316.

Film 318 may be placed on top side 312 of display panel 120. Film 318may be a protective layer for display panel 120. Depending on thedesign, display panel 120 and film 318 may also define cavity 304. Forexample, if substrate 200 has portions 208 in the form of strips, gapsmay be present between the strips. Film 318 may cover the gaps betweenthe strips in addition to the strips themselves.

Film 318 may be placed on display panel 120 at different times. Forexample, film 318 may be placed on display panel 120 prior to placingdisplay panel 120 within resin barrier 300. When placed on display panel120 prior to placing display panel 120 within resin barrier 300, film318 may be attached to display panel 120. The attachment may be madethrough an adhesive or some other suitable mechanism.

As another illustrative example, film 318 may be placed on display panel120 after resin 306 has been cured. In still other illustrativeexamples, film 318 may be omitted or removed after curing resin 306.

Further, film 318 also may act as a release film with respect to caulplate 320. In another illustrative example, film 318 may be removedafter resin 306 is cured. Another film may replace film 318. When film318 is not used, caul plate 320 may define cavity 304 along with displaypanel 120, resin barrier 300, and surface 114 within resin barrier 300.

In another illustrative example, spacing structures 204 also may belocated on top side 312 of substrate 200 and display panel 120. Spacingstructures 204 may define a portion of cavity 304 on top side 312 whencaul plate 320 is placed against display panel 120 and force 310 isapplied.

For example, spacing structures 204 on top side 312 may touch caul plate320. When film 318 is located on display panel 120, spacing structures204 may touch caul plate 320 indirectly through film 318.

As depicted, resin 306 may flow within cavity 304 to encapsulate or sealelectronic components 202 that may be found on both bottom side 302 andtop side 312 of substrate 200 for display panel 120. As a result, resin306 within cavity 304 on top side 312 may also contribute to first shape308 of display panel 120. In other words, cured resin 316 may beconsidered part of display panel 120 in addition to attaching displaypanel 120 to surface 114.

Display panel 120 with cured resin 316 may have a desired shape withrespect to surface 114. For example, the profile for the cross-sectionof surface 114 with display panel 120 may have a desired shape forperformance purposes. For example, the profile of surface 114 withdisplay panel 120 may provide a desired airflow for aircraft 104.

In still another illustrative example, film 322 may be placed on surface114 within the area defined by resin barrier 300. Film 322 may be anattachment film. For example, resin 306 may be attached to film 322. Inturn, film 322 may be selected such that film 322 attaches or sticks tosurface 114.

With this configuration, film 322 may provide separation betweenelectronic components 202 on bottom side 302 of substrate 200 andsurface 114. Further, film 322 may have features that define air gaps orchannels that are not filled by cured resin 316.

The application of film 322 may include using a surface preparation orprimer. Further, attaching display panel 120 to surface 114 may includea surface preparation or primer.

The different operations described in FIG. 3 may be performed byoperator 350. Operator 350 may be human operator. In other illustrativeexamples, operator 350 may be a robot, a robotic arm, or some othersuitable type of equipment that may be used to attach display panel 120to surface 114 of aircraft 104.

In this manner, the illustrative examples described with respect toFIGS. 1-3 provide a technical solution for attaching display panel 120to surface 114 in a manner that overcomes the technical problem ofattaching display panels to the surface of an aircraft in a manner thatreduces stresses within the display panels attached to the surface of anaircraft. Additionally, the illustrative examples also may reducestresses imparted upon aircraft structures and allow display panel 120to match the shape of surface 114 for aircraft structure 115. Matchingof the shapes may occur when the profiles match each other. The matchingoccurs such that display panel 120 may be attached to surface 114 in amanner that display panel 120 provides a desired airflow over aircraft104.

The different operations illustrated provide a technical effect thatreduces at least one of stress within display panel 120, the occurrenceof wrinkles in display panel 120, the occurrence of undesired thicknessvariation, or the occurrence of disbonds between display panel 120 andsurface 114 when display panel 120 is attached to surface 114. Thesereductions improve the overall performance of display panel 120. As aresult, less rework and maintenance may occur with the use of displaypanel 120 attached as described in FIGS. 1-3.

The illustration of information display environment 100 and thedifferent components and processes using those components in FIGS. 1-3is not meant to imply physical or architectural limitations to themanner in which an illustrative embodiment may be implemented. Othercomponents in addition to or in place of the ones illustrated may beused. Some components may be unnecessary. Also, the blocks are presentedto illustrate some functional components. One or more of these blocksmay be combined, divided, or combined and divided into different blockswhen implemented in an illustrative embodiment.

For example, electronic components 202 may include other types ofelectric components in addition to light-emitting elements 210. Forexample, electronic components 202 may include a video controller,storage, sensors, switches, processors, integrated circuits, and othersuitable electronic components for use in or with display panel 120. Inyet another illustrative example, one or more operators in addition tooperator 350 may perform operations to attach display panel 120 tosurface 114. In another illustrative example, resin barrier 300 may beformed as part of surface 114 of aircraft structure 115 when surface 114of aircraft structure 115 is formed. Additionally, in other illustrativeexamples, vehicle 102 may take other forms in addition to aircraft 104.For example, vehicle 102 may be selected from one of a spacecraft, atrain, an automobile, a bus, a surface ship, or some other suitable typeof vehicle.

In another illustrative example, resin barrier 300 may be formed as partof display panel 120. In yet another illustrative example, cured resin316 may not hold display panel 120 on surface 114. Instead, displaypanel 120 may be removed and then attached to surface 114 throughbonding using at least one of double-sided tape, adhesive, or some otherbonding system. As another illustrative example, display panel 120 maybe held on surface 114 by a mechanical attachment system such asfasteners, clips, screws, bolts, or some other suitable types ofattachment systems.

Attachment of display panel 120 may also use any combination of thefollowing mechanisms such as resin primary bonding using resin 306, tapeand secondary adhesive bonding, a mechanical attachment system, orfasteners. The mechanical attachment system may include using hooks orcured resin 316 holding mechanical attachment features. These mechanicalattachment features may be found on at least one of display panel 120 orsurface 114 of aircraft structure 115.

With reference now to FIG. 4, an illustration of an aircraft is depictedin accordance with an illustrative embodiment. In this depicted example,aircraft 400 is an example of a physical implementation for aircraft 104shown in block form in FIG. 1.

In this illustrative example, aircraft 400 has first wing 402 and secondwing 404 attached to fuselage 406. Aircraft 400 includes first engine408 attached to first wing 402 and second engine 410 attached to secondwing 404.

As depicted, fuselage 406 has nose section 412 and tail section 414.First horizontal stabilizer 416, second horizontal stabilizer 418, andvertical stabilizer 420 are attached to tail section 414 of fuselage406.

In these illustrative examples, display panels are attached to aircraft400. The display panels include display panel 422, display panel 424,display panel 426, display panel 428, and display panel 430 can be seenon aircraft 400. These display panels are examples of physicalimplementations for the number of display panels 112 shown in block formin FIG. 1.

As depicted, display panel 422, display panel 424, display panel 426,display panel 428, and display panel 430 are mounted on exterior surface440 of aircraft 400. In particular, display panel 422, display panel424, display panel 426, display panel 428, and display panel 430 aremounted to be substantially flush to exterior surface 440 of aircraft400. In other words, display panel 422, display panel 424, display panel426, display panel 428, and display panel 430 may be embedded withinexterior surface 440 of aircraft 400. In this manner, undesired airflowon aircraft 400 may be reduced or avoided.

In other illustrative examples, display panels may be located in otherlocations in addition to or in place of the locations shown in FIG. 4.For example, display panels may be in locations such as on top surfaces,leading edges, trailing edges, lateral edges, or other locations thatare flush with existing structures to provide desired airflow forsurfaces.

As depicted, display panel 422 is located on second wing 404; displaypanel 424 is located on fuselage 406; display panel 426 is located onsecond engine 410; and display panel 428 is located on first wing 402,while display panel 430 is located on vertical stabilizer 420. Theillustration of display panel 422, display panel 424, display panel 426,display panel 428, and display panel 430 on aircraft 400 in FIG. 4 isonly an example of some locations where display panel 422, display panel424, display panel 426, display panel 428, and display panel 430 may belocated.

Additional display panels also may be present on aircraft 400, but notseen in this view. For example, a display panel also may be located onfirst engine 408, fuselage 406, the underside of second wing 404, theother side of vertical stabilizer 420, or in some other suitablelocation on aircraft 400. If winglets are used on wings, the displaypanel may be located on the winglet. In yet another example, anotherdisplay panel may be located on the other side of fuselage 406 oppositeto display panel 424 as seen on fuselage 406 upon other structures notseen in this view.

FIGS. 5-14 illustrate operations performed to attach a display panel tothe surface of an aircraft structure in accordance with an illustrativeembodiment. Turning first to FIG. 5, an illustration of an aircraftstructure is depicted in accordance with an illustrative embodiment. Inthis illustrative example, display panel 500 is attached to surface 502of aircraft structure 504. As depicted, aircraft structure 504 is wing506 for an aircraft. Wing 506 is a composite wing in this illustrativeexample. In other examples, wing 506 may be a metal wing.

Display panel 500 is attached to wing 506 prior to wing 506 beingattached the fuselage of an aircraft. In other illustrative examples,display panel 500 may be attached to wing 506 after wing 506 is attachedto the aircraft. In another illustrative example, display panel 500 maybe attached during a joining process for the wing and aircraft.

In FIG. 6, an illustration of preparing a wing to receive a displaypanel is depicted in accordance with an illustrative embodiment. In thisexample, resin barrier 600 is formed on surface 502 of aircraftstructure 504.

As depicted, resin barrier 600 is formed by robotic arm 602 with endeffector 604 depositing polymer material 606 onto surface 502 to formresin barrier 600. As depicted, resin barrier 600 has perimeter wall 601and surface layer 603. The shape of resin barrier 600 corresponds to theperiphery of display panel 500 such that display panel 500 may be placedwithin perimeter wall 601 of resin barrier 600.

As depicted, perimeter wall 601 may be used in conjunction with displaypanel 500 to define a cavity. In this example, perimeter wall 601 ofresin barrier 600 may prevent resin from flowing out of the cavity whenresin is placed into the cavity.

In this illustrative example, surface layer 603 is optional and mayperform different functions. For example, surface layer 603 may have afunction selected from at least one of a barrier to keep resin fromcontacting surface 502 of wing 506, an insulator for electroniccomponents in display panel 500, or other suitable functions. Resinbarrier 600 may prevent or reduce leaks through surface 502 of aircraft400.

In the illustrative example, display panel 500 may be a single structureor formed from multiple panels connected to each other. In a similarfashion, resin barrier 600 may be a single part or formed from severalparts.

With reference now to FIG. 7, an illustration of positioning a displaypanel is depicted in accordance with an illustrative embodiment. In thisfigure, display panel 500 has been positioned within perimeter wall 601of resin barrier 600 by human operator 702. Additionally, film 700 hasbeen placed on display panel 500.

Turning to FIG. 8A, an illustration of the positioning of a caul plateis depicted in accordance with an illustrative embodiment. In thisdepicted example, robotic arm 602 has end effector 800 that holdsbladder 801 and caul plate 802. As seen in this example, caul plate 802is positioned on film 700 and display panel 500. In this example, humanoperator 702 is shown injecting resin into the cavity through perimeterwall 601 of resin barrier 600 using syringe 804.

This positioning of display panel 500 within resin barrier 600, film700, and caul plate 802 defines a cavity (not shown). Film 700 isoptional in this illustrative example.

As depicted, robotic arm 602 manipulates caul plate 802 to apply a forceon film 700 and display panel 500 with the resin within the cavity. Inthis illustrative example, force is applied when bladder 801 is inflatedwith a fluid. The inflation of bladder 801 causes caul plate 802 toapply force on display panel 500 with film 700 located between caulplate 802 and display panel 500. Bladder 801 may be pressurized usingany fluid. Also, the fluid may be cooled or heated to change the curetime for the resin.

The force is applied such that display panel 500 is in a desired shapewith respect to surface 502 to an aircraft structure 504. For example,if aircraft structure 504 has a curve in the profile, display panel 500has a corresponding curve in the profile of display panel 500. In thisillustrative example, the resin is cured with the force being appliedusing caul plate 802.

In this example, film 700 is shown as being placed in display panel 500.In another illustrative example, film 700 may be located on caul plate802 and positioned on display panel 500 when caul plate 802 ispositioned on display panel 500.

With reference now to FIG. 8B, an illustration of the placement of asyringe in a resin barrier is depicted in accordance with anillustrative embodiment. As depicted, an enlarged view of human operator702 is shown in FIG. 8A. In this view, syringe 804 is shown as beinginserted through resin barrier 600 into the cavity (not shown). Thisplacement of syringe 804 occurs after caul plate 802 is in place. Inthis manner, resin may be injected into the cavity.

With reference now to FIG. 9, an illustration of a display panelattached to an aircraft structure is depicted in accordance with anillustrative embodiment. In this example, the resin has been cured andcaul plate 802 has been moved away from display panel 500.

In this particular example, resin barrier 600 remains after attachmentof display panel 500. In another illustrative example, at least one ofresin barrier 600 or film 700 may be removed. In this manner, desiredairflow and other performance properties may be present when displaypanel 500 is attached to aircraft structure 504.

Turning to FIG. 10, an illustration of a cross-section of a displaypanel is depicted in accordance with an illustrative embodiment. In thisillustrative example, a cross-sectional view of display panel 500 isshown taken along lines 10-10 in FIG. 5.

In this view, display panel 500 includes substrate 1000. As depicted,substrate 1000 is comprised of strip 1002 and strip 1004.

In this illustrative example, strip 1002 and strip 1004 are flexiblestrips with gap 1005 between strip 1002 and strip 1004. As depicted, theflexible strips may bend to conform to a surface of an aircraftstructure without undesired stresses occurring in the flexible strips.

Light-emitting elements 1006 are shown on top side 1008 of substrate1000 in display panel 500. Light-emitting elements 1006 includelight-emitting element 1009, light-emitting element 1010, light-emittingelement 1012 and light-emitting element 1014.

As depicted in this sectional view, spacing elements 1016 are present onbottom side 1018 of substrate 1000. In this view, spacing elements 1016include spacing element 1019, spacing element 1020, spacing element1022, spacing element 1024, spacing element 1026, and spacing element1028. The spacing elements are configured to cause display panel 500 tohave a desired shape when attached to surface 502 of aircraft structure504.

In this illustrative example, spacing elements 1016 are only shown onbottom side 1018 of substrate 1000. In the illustrative example, spacingelements 1016 may be at least one of electronic elements or structuralelements in display panel 500. Light-emitting elements 1006 on top side1008 of substrate 1000 also may function as spacing elements 1016 inaddition to providing a display of information.

With reference next to FIG. 11, an illustration of a cross-section of adisplay panel positioned on a resin barrier and an aircraft structure isdepicted in accordance with an illustrative embodiment. As depicted inthis figure, a cross-sectional view of display panel 500 positionedadjacent to resin barrier 600 on surface 502 of aircraft structure 504is shown taken along lines 11-11 in FIG. 8A.

The positioning of display panel 500 within resin barrier 600 formscavity 1100. As shown, cavity 1100 is defined by display panel 500, film700, resin barrier 600, and surface 502.

As can be seen in this view, caul plate 802 is positioned over displaypanel 500, but is not applying force to display panel 500. Display panel500 has a first shape that is substantially planar. Surface 502 has asecond shape that is curved. As can be seen, gap 1101 and gap 1102 arepresent between bottom side 1018 of display panel 500 and surface 502 ofaircraft structure 504.

As depicted, spacing element 1022 and spacing element 1024 touch surface502. However, spacing element 1019, spacing element 1020, spacingelement 1026, and spacing element 1028 do not touch surface 502.

Turning next to FIG. 12, an illustration of a cross-section of a displaypanel positioned within a resin barrier and an aircraft structure with aforce applied to the display panel is depicted in accordance with anillustrative embodiment. Another cross-sectional view of display panel500 positioned within resin barrier 600 on surface 502 of aircraftstructure 504 is shown taken along lines 11-11 in FIG. 8A. In this view,force is applied by caul plate 802 in the direction of arrow 1200. Inthis cross-sectional view, the force applied by caul plate 802 causesspacing element 1019, spacing element 1020, spacing element 1022,spacing element 1024, spacing element 1026, and spacing element 1028 totouch surface 502.

As shown in this figure, the force applied by caul plate 802 causesdisplay panel 500 to bend. This bending causes the first shape ofdisplay panel 500 to change and conform to the second shape of surface502. In other words, display panel 500 now has a curve that issubstantially similar to the curve of surface 502.

Additionally, light-emitting elements 1006 on top side 1008 of substrate1000 also function as spacing elements 1016. In this example,light-emitting elements 1006 touch mating surface 1202 on caul plate 802when display panel 500 bends. As depicted, light-emitting elements 1006touch caul plate 802 indirectly through film 700.

Turning next to FIG. 13, an illustration of a cross-section of resin ina cavity of a display panel while a force is applied to the displaypanel is depicted in accordance with an illustrative embodiment. Across-sectional view of display panel 500 positioned within resinbarrier 600 on surface 502 of aircraft structure 504 is shown takenalong lines 11-11 in FIG. 8A.

In this view, resin 1300 has been injected into cavity 1100. Resin 1300is present on both top side 1008 and bottom side 1018 through gap 1005between strip 1002 and strip 1004 in display panel 500. In this view,resin 1300 encapsulates light-emitting elements 1006.

With reference next to FIG. 14, an illustration of a cross-section ofcured resin in a cavity of a display panel is depicted in accordancewith an illustrative embodiment. A cross-sectional view of display panel500 positioned within resin barrier 600 on surface 502 of aircraftstructure 504 is shown taken along lines 14-14 in FIG. 9.

When resin 1300 is cured to form cured resin 1400, cured resin 1400 mayprotect light-emitting elements 1006, insulate light-emitting elements1006, or provide some other function.

Cured resin 1400 holds display panel 500 in the first shape thatsubstantially conforms to the second shape of surface 502. In otherwords, display panel 500 has a shape that changes to the first shape tomatch the second shape. With the use of caul plate 802 applying a forceon display panel 500, display panel 500 may be attached to surface 502with a desired shape.

Additionally, this process also reduces at least one of the presence ofwrinkles, disbonds, undesired thickness variation, or stresses that maybe present with display panel 500 being a flexible display panel.

In FIG. 15, an illustration of mechanical attachment features isdepicted in accordance with an illustrative embodiment. In thisillustrative example, surface 1500 is a surface for an aircraftstructure on which the display panel is to be attached. Spacing element1502 is an example of a spacing element that may be used on displaypanel 1504.

As depicted, spacing element 1502 includes mechanical attachment feature1506. Additionally, surface 1500 has mechanical attachment feature 1508.

During attachment of the display panel 1504 to surface 1500, resin 1510flows around mechanical attachment feature 1506 and mechanicalattachment feature 1508. When resin 1510 is cured, the resin 1510 inthis cured form mechanically attaches display panel 1504 to surface 1500through mechanical attachment feature 1506 and mechanical attachmentfeature 1508. This mechanical attachment may be in addition to a bondthat may be generated between the resin and the display panel. Forexample, fasteners, double-sided tape, adhesive, or other mechanisms maybe used.

In this illustrative example, air gap 1512 and air gap 1514 are present.These air gaps may allow for some movement in a manner that producesstress within display panel 1504. These air gaps are optional.

The air gaps may be filled with a material such as a polymer, anelastomer, or some other suitable material. As depicted, the material inthe air gaps is softer than resin 1510 when resin 1510 is cured. In thismanner, the air gaps may be filled and may allow surface 1500 of theaircraft structure to move with respect to display panel 1504. In othercases, the material may be selected for use in resin 1510 that alsoreduces stress within display panel 1504.

The illustration of the display panels in different features in FIGS.4-15 are presented only as examples of some implementations forattaching display panels to the surfaces of aircraft structures. Theseillustrations are not meant to limit the manner in which otherillustrative examples may be implemented. For example, spacingstructures may be used on a top side of the display panel in addition toor in place of using display elements as spacing structures. In anotherexample, spacing structures may be located on both sides of a displaypanel and may comprise any number of components and structures that formthe display panel.

In still other illustrative examples, other devices other than displayelements may function as spacing structures on the top side of a displaypanel. In another illustrative example, electronic components may bepresent on the bottom side of a display panel. These electroniccomponents and the bottom side may function as spacing structures insome illustrative examples. As another example, the display panel has asubstrate that is a single strip rather than multiple strips.

The process illustrated in FIGS. 4-15 may be used to attach displaypanel 500 to structures other than an aircraft structure in the form ofa wing. For example, display panel 500 may be attached to a verticalstabilizer, a winglet, an engine housing, a fuselage, a fairing, orother aircraft structures in a similar manner.

In yet another illustrative example, a crawler may be used in place ofrobotic arm 602. For example, a crawler may hold caul plate 802 andbladder 801.

As another example, caul plate 802 and bladder 801 may be held in placeusing a number of straps or other mechanism that holds caul plate 802and bladder 801 in place with respect to aircraft structure 504. Inother illustrative examples, display panel 500 may be bent to becomesubstantially flat when surface 502 is substantially flat.

With reference now to FIG. 16, an illustration of a flowchart of aprocess for conforming a display panel is depicted in accordance with anillustrative embodiment. The process illustrated in FIG. 16 may beimplemented in information display environment 100 in FIG. 1. Inparticular, the process may be implemented for use in attaching displaypanel 120 to surface 114 of vehicle 102.

The process begins by positioning a display panel within a resin barrierand against a surface of a structure (operation 1600). The positioningis such that a bottom side of the display panel is against the surfaceof the aircraft structure.

A force is applied on the display panel that is sufficient to causespacing structures on the display panel to touch the surface of thestructure such that the display panel has a shape that changes to afirst shape to match a second shape of the surface of the structure(operation 1602). In this manner, the display panel is conformed to thesurface of the structure. Also, in operation 1602, the desired shape maybe a first shape that substantially conforms to a second shape of thesurface of the aircraft. In other illustrative examples, the desiredshape may not substantially conform to or match a second shape of thesurface, but may form an aerodynamic structure that generates a desiredairflow when the vehicle is an aircraft in flight.

The spacing structures touching the surface of the aircraft structure inoperation 1602 may be an indirect touching in some illustrativeexamples. For example, when the resin barrier includes both a perimeterwall and a surface layer, the surface layer is located between thespacing structures and the surface of the structure. The first shape ofthe display panel is a shape that is the same as the second shape of thesurface of the vehicle. In the illustrative example, the first shape maybend to match the second shape.

The process then places a resin into a cavity defined by the displaypanel positioned within the resin barrier and against the surface of theaircraft structure (operation 1604). The cavity may also be defined bythe caul plate, the film, the release ply, or other structures that maybe used in attaching the display panel to the surface of the aircraft.The display panel may include spaces or volumes that are part of thecavity. The process cures the resin while the force is applied to thedisplay panel to form a cured resin that holds the display panel in thefirst shape (operation 1606).

In operation 1606, the display panel has a shape that conforms to theshape of the surface of the vehicle. The conformation results in theshapes being matched. The cured resin may also hold the display panel tothe surface of the vehicle in some illustrative examples.

The process then attaches the display panel in the first shape to thesurface of the structure (operation 1608) with the process terminatingthereafter. The attachment may be made using a number of differentmechanisms. For example, at least one of double-sided tape, adhesive,fasteners, or other suitable attachment mechanisms may be used.

Attachment of display panel 120 may also use any combination of thefollowing mechanisms such as resin primary bonding using resin 306, tapeand secondary adhesive bonding, a mechanical attachment system, orfasteners. Mechanical attachment systems may include using hooks orcured resin 316 holding mechanical attachment features. These mechanicalattachment features may be found on at least one of display panel 120 orsurface 114 of aircraft structure 115.

With reference next to FIG. 17, an illustration of a flowchart of aprocess for conforming and attaching a display panel to the surface ofan aircraft is depicted in accordance with an illustrative embodiment.The process illustrated in FIG. 17 may be implemented in informationdisplay environment 100 in FIG. 1.

The process begins by forming a resin barrier on a surface of anaircraft (operation 1700). The process places the display panel withinthe resin barrier such that a cavity is formed (operation 1702). In thisoperation, the cavity is an open cavity that is not fully enclosed bystructures. In other words, the cavity may have one or more openings.

A film is placed on a caul plate (operation 1704). The caul plate ismoved against the display panel (operation 1705). In operation 1702, thecavity may become a closed cavity when openings are not present.Additionally, in operation 1704, a bladder may also be moved with thecaul plate against the display panel.

A force is applied on the film and the display panel through the caulplate that causes the display panel to conform to the surface of theaircraft (operation 1706). The process injects a resin into the cavitywhile the force is applied (operation 1708). The process cures the resinin the cavity while the force is applied to form a cured resin(operation 1710). The shape of the display panel conforms to the shapeof the surface of the aircraft. The cured resin causes the display panelto maintain the shape. The cured resin may also hold the display panelon the surface of the aircraft.

The process removes the resin barrier after curing the resin (operation1712). The process then attaches the display panel to the surface(operation 1714). In this case, double-sided tape, adhesive, fasteners,other devices, or some combination thereof may be used to attach thedisplay panel to the surface of the aircraft. The process terminatesthereafter.

The film on the caul plate may be a protective film for the displaypanel that remains attached to the display panel. Alternatively, thefilm may be a release film that is removed.

With reference to FIG. 18, an illustration of a flowchart of a processfor applying a force on a display panel is depicted in accordance withan illustrative embodiment. The process illustrated in FIG. 18 is anexample of an implementation for operation 1708 in FIG. 17.

The process begins by positioning a caul plate on the display panel(operation 1800). In operation 1800, the caul plate may include abladder. Also, in operation 1800, the film is located on the caul plate.The process applies the force on the display panel through the film tocause the display panel to conform to the surface of the aircraft with acaul plate positioned against the film and the display panel (operation1802) with the process terminating thereafter.

The flowcharts and block diagrams in the different depicted embodimentsillustrate the architecture, functionality, and operation of somepossible implementations of apparatuses and methods in an illustrativeembodiment. In this regard, each block in the flowcharts or blockdiagrams may represent at least one of a module, a segment, a function,or a portion of an operation or step. For example, one or more of theblocks may be implemented as program code, in hardware, or a combinationof the program code and hardware. For example, some the operations maybe implemented using robotic arms, automated manufacturing equipment, orother suitable devices. When implemented in hardware, the hardware may,for example, take the form of integrated circuits that are manufacturedor configured to perform one or more operations in the flowcharts orblock diagrams. When implemented as a combination of program code andhardware, the implementation may take the form of firmware.

In some alternative implementations of an illustrative embodiment, thefunction or functions noted in the blocks may occur out of the ordernoted in the figures. For example, in some cases, two blocks shown insuccession may be performed substantially concurrently, or the blocksmay sometimes be performed in the reverse order, depending upon thefunctionality involved. Also, other blocks may be added in addition tothe illustrated blocks in a flowchart or block diagram.

In some illustrative examples, operation 1608 may be omitted from theflowchart in FIG. 16. The curing of the resin may result in the displaypanel being attached to the surface of the aircraft structure.Mechanical attachment features such as those shown in FIG. 15 may beused.

As another example, the film may be placed on an optionally cureddisplay panel prior to placing the display panel within the resinbarrier in FIG. 17. In other illustrative examples, the operations mayplace the film and the display panel together instead of the film beinglocated on the caul plate. This placement may occur when the film has athickness that is applied in a manner that does not result in wrinkleswhen placed on the display panel.

As another example, finishing operations may be performed after removingthe resin barrier in operation 1712. In another illustrative example,operation 1712 may be omitted.

In still another example, the process in FIG. 16 may include otheroperations such as secondary bonding of the display panel to theaircraft. Additional operations may include bonding the display panel tothe aircraft with tape or connecting the display panel to the aircraftusing fasteners. For example, the display panel may be attached to thesurface through bonding using at least one of double-sided tape,adhesive, or some other bonding system. As another illustrative example,the display panel may be held on the surface by a mechanical attachmentsystem such as fasteners, clips, screws, bolts, or some other suitabletypes of attachment systems. Attachment of display panel 120 may alsouse any combination of the following mechanisms such as resin primarybonding using a resin, a tape, secondary adhesive bonding, mechanicalattachment, or fasteners. Mechanical attachments may include hooks orcured resin 316 holding mechanical attachment features.

In yet another example, an operation may be added to the flowchart inFIG. 17 after operation 1712 that places a film on an exterior surfaceof the display panel. This film may be a protective layer and may extendbeyond the display panel surface and onto the surface of the aircraft.The film may function as a barrier to the environment, an air flowmodifier, a static charge dissipater, or a surface protector. Thesurface protectant may protect against surface abrasion, ultravioletlight, or other undesired environmental impingement. For example, thefilm may be a protective film that reduces or prevents moisture fromreaching the interior of the display panel.

As an additional example, operation 1714 may be omitted when the curedresin also functions to attach the display panel to the surface of theaircraft. Operation 1714 may also be used to provide additional strengthor durability in attaching the display panel to the surface of theaircraft.

Illustrative embodiments of the disclosure may be described in thecontext of aircraft manufacturing and service method 1900 as shown inFIG. 19 and aircraft 2000 as shown in FIG. 20.

Turning first to FIG. 19, an illustration of a block diagram of anaircraft manufacturing and service method is depicted in accordance withan illustrative embodiment. During pre-production, aircraftmanufacturing and service method 1900 may include specification anddesign 1902 of aircraft 2000 in FIG. 20 and material procurement 1904.

During production, component and subassembly manufacturing 1906 andsystem integration 1908 of aircraft 2000 in FIG. 20 takes place.Thereafter, aircraft 2000 in FIG. 20 may go through certification anddelivery 1910 in order to be placed in service 1912. While in service1912 by a customer, aircraft 2000 in FIG. 20 is scheduled for routinemaintenance and service 1914, which may include modification,reconfiguration, refurbishment, and other maintenance or service.

Each of the processes of aircraft manufacturing and service method 1900may be performed or carried out by at least one system integrator, athird party, or an operator. In these examples, the operator may be acustomer. For the purposes of this description, a system integrator mayinclude, without limitation, any number of aircraft manufacturers andmajor-system subcontractors; a third party may include, withoutlimitation, any number of vendors, subcontractors, and suppliers; and anoperator may be an airline, a leasing company, a military entity, aservice organization, an individual, and so on.

With reference now to FIG. 20, an illustration of a block diagram of anaircraft is depicted in which an illustrative embodiment may beimplemented. In this example, aircraft 2000 is produced by aircraftmanufacturing and service method 1900 in FIG. 19 and may includeairframe 2002 with plurality of systems 2004 and interior 2006. Examplesof systems 2004 include one or more of propulsion system 2008,electrical system 2010, hydraulic system 2012, and environmental system2014. Any number of other systems may be included. Although an aerospaceexample is shown, different illustrative embodiments may be applied toother industries, such as the automotive industry.

Apparatuses and methods embodied herein may be employed during at leastone of the stages of aircraft manufacturing and service method 1900 inFIG. 19. In one illustrative example, components or subassembliesproduced in component and subassembly manufacturing 1906 in FIG. 19 maybe fabricated or manufactured in a manner similar to components orsubassemblies produced while aircraft 2000 is in service 1912 in FIG.19. As yet another example, one or more apparatus embodiments, methodembodiments, or a combination thereof may be utilized during productionstages, such as component and subassembly manufacturing 1906 and systemintegration 1908 in FIG. 19. One or more apparatus embodiments, methodembodiments, or a combination thereof may be utilized while aircraft2000 is in service 1912, during maintenance and service 1914, or bothwhile aircraft 2000 is in service 1912 and during maintenance andservice 1914 in FIG. 19. For example, display panels installed onaircraft 2000 may be used during these phases. The use of a number ofthe different illustrative embodiments may substantially expedite theassembly, reduce the cost, or expedite assembly and reduce cost ofaircraft 2000.

The description of the different illustrative embodiments has beenpresented for purposes of illustration and description and is notintended to be exhaustive or limited to the embodiments in the formdisclosed. The different illustrative examples describe components thatperform actions or operations. In an illustrative embodiment, acomponent may be configured to perform the action or operationdescribed. For example, the component may have a configuration or designfor a structure that provides the component an ability to perform theaction or operation that is described in the illustrative examples asbeing performed by the component.

This, the examples provided method and apparatus for attaching a displaypanel to the surface of an aircraft in the desired manner. In oneillustrative example, the display panel is attached in a manner thatreduces stress, wrinkling, disbonds, or some combination thereof in thedisplay panel. A resin barrier is formed on a surface of an aircraftstructure. The display panel is positioned within the resin barrierformed on the surface of the aircraft structure. In some cases, theresin barrier may be part of the display panel. In other examples, theresin barrier may be part of the caul plate or the resin barrier may bepart of the film. A resin is placed into a cavity defined by the displaypanel positioned within the resin barrier. A force is applied on thedisplay panel that is sufficient to cause spacing structures on thedisplay panel to touch the surface of the aircraft structure such thatthe display unit has a desired shape. The shape may result in a desiredsurface profile when the display panel is attached to the surface of theaircraft structure. The resin is cured while the force is applied to thedisplay panel to form a cured resin that may encapsulate the displaypanel. The encapsulation may be a full or partial encapsulation of thedisplay panel. For example, a partial encapsulation may only fill thecavity. As another example, a partial encapsulation may fill the cavityand cover a portion of the top of the display panel. The structureformed by the cured resin and the display panel may be attached to thesurface of the aircraft structure with the first shape.

The force is applied while the display panel is held in place within theresin barrier. With the force, these components, along with the surfaceof the aircraft structure, form the shape of the display panel that maybe encapsulated and maintained by the cured resin. With this shape, thedisplay panel may be attached by the cured resin to the aircraft andother attachment mechanisms after curing, or the display panel may becured, removed, and attached at a later time to the surface of theaircraft structure at the same location.

Thus, one or more of the illustrative examples overcome the technicalproblem of attaching display panels to the surface of an aircraft in amanner that reduces stresses to the display panels attached to thesurface of an aircraft. The illustrative examples may also reduce atleast one of profile mismatches, stress wrinkles, disbonds, undesiredthickness variations, or other undesired conditions for the displaypanel. As a result, less rework and maintenance may occur. Also,improved display panel and aircraft performance, fit, and finish alsomay result from using a display panel attached to an aircraft in anillustrative example.

The description of the different illustrative embodiments has beenpresented for purposes of illustration and description and is notintended to be exhaustive or limited to the embodiments in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. Further, different illustrativeembodiments may provide different features as compared to otherdesirable embodiments. The embodiment or embodiments selected are chosenand described in order to best explain the principles of theembodiments, the practical application, and to enable others of ordinaryskill in the art to understand the disclosure for various embodimentswith various modifications as are suited to the particular usecontemplated.

What is claimed is:
 1. A method for conforming a display panel to asurface of an aircraft structure, the method comprising: positioning thedisplay panel within a resin barrier that is located on the surface suchthat a cavity is formed; applying a force on the display panel thatcauses the display panel to conform to the surface of the aircraftstructure, wherein the display panel has a shape that changes to a firstshape to match a second shape of the surface of the aircraft structure;injecting a resin into the cavity while the force is applied; and curingthe resin in the cavity while the force is applied to form a curedresin, wherein the cured resin holds the display panel in the firstshape and attaches the display panel to the surface of the aircraftstructure.
 2. The method of claim 1 further comprising: attaching thedisplay panel to the surface of the aircraft structure.
 3. The method ofclaim 1 further comprising: forming the resin barrier on the surface ofthe aircraft structure.
 4. The method of claim 1 further comprising:placing a film and the display panel together, wherein placing the filmand the display panel together comprises: positioning a caul plateagainst the display panel, wherein the film is located on the caulplate.
 5. The method of claim 1, wherein the applying step comprises:positioning a caul plate against the display panel; and applying theforce on the display panel that causes the display panel to conform tothe surface of the aircraft structure with the caul plate positionedagainst the display panel.
 6. The method of claim 1, wherein the forcecauses spacing structures on the display panel to touch the surface ofthe aircraft structure to cause the display panel to conform to thesurface of the aircraft structure.
 7. The method of claim 1, wherein acaul plate has a mating surface with a release layer on the matingsurface that contacts the display panel.
 8. The method of claim 1further comprising: removing the resin barrier after curing the resin.9. The method of claim 1, wherein the resin barrier is comprised of amaterial selected from at least one of a polymer, an insulating polymer,a film adhesive, a gel coat, an elastomer, an insulating elastomer, or aprimer.
 10. The method of claim 1, wherein the resin is selected from atleast one of a substantially transparent resin, a thermoset resin, anepoxy, a polyimide, a polyurethane, a silicone, an acrylic, or aphenolic.
 11. The method of claim 1, wherein the display panel is aflexible display panel having the shape that changes to the first shapethat is substantially the same as the second shape of the surfacewithout an undesired amount of stress imparted within the display panel.12. The method of claim 1, wherein the display panel compriseslight-emitting elements.
 13. The method of claim 1, wherein the resinbarrier is part of the display panel and is located on the surface whenthe display panel with the resin barrier is positioned on the surface.14. A method for conforming a display panel comprising: positioning thedisplay panel within a resin barrier and against a surface of astructure such that a bottom side of the display panel is against thesurface of the structure; placing a resin into a cavity defined by thedisplay panel positioned within the resin barrier and against thesurface of the structure; applying a force on the display panel that issufficient to cause spacing structures on the display panel to touch thesurface of the structure such that the display panel has a shape thatchanges to a first shape to match a second shape of the surface of thestructure; and curing the resin while the force is applied to thedisplay panel to form a cured resin that holds the display panel in thefirst shape.
 15. The method of claim 14, wherein the cured resinattaches the display panel to the surface of the structure.
 16. Themethod of claim 14 further comprising: attaching the display panel inthe first shape to the surface of the structure.
 17. The method of claim14 further comprising: forming the resin barrier on the surface of thestructure prior to placing the resin in the cavity.
 18. The method ofclaim 14 further comprising: placing a film on a top side of the displaypanel.
 19. The method of claim 17, wherein the forming step comprises:positioning the display panel on the surface of the structure, whereinthe resin barrier is a part of the display panel.
 20. The method ofclaim 14, wherein the resin is a substantially transparent resin. 21.The method of claim 14, wherein the resin barrier is a part of thesurface of the structure.
 22. The method of claim 14, wherein the resinbarrier is comprised of a material selected from at least one of apolymer, an insulating polymer, a film adhesive, a gel coat, anelastomer, an insulating elastomer, or a primer.
 23. The method of claim14, wherein the resin is selected from at least one of a substantiallytransparent resin, a thermoset resin, an epoxy, a polyimide, apolyurethane, a silicone, an acrylic, or a phenolic.
 24. The method ofclaim 14, wherein the display panel is a flexible display panel thatbends such that a desired shape is the first shape that is substantiallythe same as the second shape of the surface without an undesired amountof stress imparted within the display panel.
 25. The method of claim 14,wherein the display panel comprises a substrate and light-emittingelements associated with the substrate.
 26. The method of claim 14,wherein the resin barrier is part of the display panel and is located onthe surface when the display panel is positioned on the surface.
 27. Themethod of claim 14, wherein the structure is for a vehicle selected fromone of an aircraft, a spacecraft, a train, an automobile, a bus, and asurface ship.
 28. An apparatus comprising: a display panel havingstructures on a bottom side that are against a surface of an aircraftstructure, wherein the structures cause the display panel to have adesired shape when the structures are against the surface of theaircraft structure; a film attached to a top side of the display panel;and a cured resin that attaches the display panel to the surface of theaircraft structure, wherein the cured resin fills a cavity defined bythe film, the display panel, the surface of the aircraft structure, anda resin barrier, and the cured resin holds the display panel in thedesired shape.
 29. The apparatus of claim 28, wherein the display panelis a flexible display panel that bends to have a first shape that issubstantially the same as a second shape of the surface without anundesired amount of stress imparted within the display panel.
 30. Theapparatus of claim 28, wherein the display panel compriseslight-emitting elements associated with a substrate.